GATE_AE_2027_MOCK_02_Q42 GATE 2027 Aerospace Engineering All-India Master Mock 02 (Compressible Aerodynamics & High-Speed Propulsion) NAT · 2 Marks
Aerodynamics & Fluid Mechanics • Compressible Flow & Shocks • Normal & Oblique Shock Waves

A uniform supersonic stream of air ($\gamma = 1.4$) at Mach $M_1 = 2.50$ encounters a 2D wedge of semi-vertex angle $\theta = 15^\circ$. If the resulting oblique shock wave angle is $\beta = 36.94^\circ$, what is the upstream Mach component normal to the shock wave, $M_{n1}$? (Round to two decimal places).

Answer Key:
1.50

Step-by-Step Verified Solution

### Solution: $M_{n1} = M_1 \sin\beta = 2.50 \times \sin(36.94^\circ) = 2.50 \times 0.60098 \approx 1.502 \approx 1.50$. Correct: 1.50 (range 1.48 to 1.52).
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